利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

136 条记录 (耗时 0.016 秒)

    CENTRIFUGAL RADIAL TURBINE
    2.
    发明申请
    CENTRIFUGAL RADIAL TURBINE 审中-公开

    公开(公告)号：US20170107818A1

    公开(公告)日：2017-04-20

    申请号：US15127921

    申请日：2015-03-17

    申请人： EXERGY S.P.A.

    发明人： Claudio SPADACINI ,  Dario RIZZI

    IPC分类号： F01D1/06 ,  F01D1/28 ,  F01K7/16

    CPC分类号： F01D1/06 ,  F01D1/14 ,  F01D1/28 ,  F01K7/16 ,  F01K25/08

    摘要： A centrifugal radial turbine includes at least one support disc having a first face bearing at least one radial rotor stage formed by an array of blades arranged in succession along a respective circular path. The disc has through induction channels situated in a position radially external with respect to a respective shaft and radially internal with respect to the radial rotor stage. At the respective through induction channels, the disc includes a plurality of induction rotor blades of at least one respective axial rotor stage.

    Turbine powerplant having rotors with concentric rows of impeller blades
    3.
    发明授权
    Turbine powerplant having rotors with concentric rows of impeller blades 失效
    涡轮动力装置具有同心排的叶轮叶片的转子

    公开(公告)号：US6032458A

    公开(公告)日：2000-03-07

    申请号：US957015

    申请日：1997-10-24

    申请人： Robert G. James

    发明人： Robert G. James

    IPC分类号： F01D1/28 ,  F02C3/05 ,  F02C3/14

    CPC分类号： F01D1/28 ,  F02C3/14 ,  Y02T50/672

    摘要： A turbocompressor assembly includes a first rotor stage mounted on a rotary shaft and including circular rows of impeller blades on one surface thereof separated by radial gaps in which opposed blade rows on a second rotor stage are received. The two rotor stages are geared for counter-rotation and at least one of the rotors is perforated proximate its center to allow air to be drawn between the opposed surfaces thereof, where its passage over the impeller blades develops useful torque. The opposed rotor surfaces are convolved to define a radially decreasing separation to an annular combustion cavity, and thereafter increasing with radius. Thus a radial compressor and a turbine function are developed by the respective blade rows on either side of the combustion cavity. The combustion cavity may be formed in one of the rotors, or may be shared between the rotors as a communicating common annular chamber. Fuel may be delivered to the combustion chamber directly admixed into the air stream, or by a fuel delivery system.

    摘要翻译： 涡轮压缩机组件包括安装在旋转轴上的第一转子级，并且在其一个表面上包括圆形排的叶轮叶片，该叶轮叶片由径向间隙分开，其中第二转子台上的相对的叶片排被接收。 两个转子级用于反向旋转，并且至少一个转子靠近其中心穿孔，以允许空气在其相对的表面之间被拉伸，其中通过叶轮叶片的通道产生有用的扭矩。 相对的转子表面被卷绕以限定到环形燃烧腔的径向减小的间隔，然后以半径增加。 因此，径向压缩机和涡轮机功能由在燃烧腔的任一侧上的各个叶片排开发。 燃烧腔可以形成在一个转子中，或者可以作为连通的公共环形室共享在转子之间。 燃料可以被输送到直接混入空气流中的燃烧室，或通过燃料输送系统。

    Disc-type airborne vehicle and radial flow gas turbine engine used therein
    4.
    发明授权
    Disc-type airborne vehicle and radial flow gas turbine engine used therein 失效
    其中使用的盘式机载车辆和径流式燃气涡轮发动机

    公开(公告)号：US4193568A

    公开(公告)日：1980-03-18

    申请号：US842673

    申请日：1977-10-17

    申请人： Norman L. Heuvel

    发明人： Norman L. Heuvel

    IPC分类号： B64C39/00 ,  F01D1/28 ,  F01D5/04 ,  B64C29/04 ,  F02C3/14

    CPC分类号： F01D1/28 ,  B64C29/0066 ,  B64C39/001 ,  F01D5/041 ,  F02C3/05

    摘要： An annular, radial flow gas turbine engine and airborne vehicle utilizing same for jet propulsion. The engine comprises counter-rotating rotors and a compressor section with counter-rotating annular rows of intermeshing compressor blades, an annular combustion section common to both rotors wherein the combustion zone is defined by oppositely rotating rotor walls, and a turbine section made up of annular rows of counter-rotating exhaust turbine blades. No stator blades are present in either the compressor or the turbine sections.The craft comprises a central hub on which the engine rotors rotate on thrust bearings, and air bearings maintain rotor tolerances with respect to each other and to nonrotating shell portions above and below the engine rotors. Air inlet guide vanes leading to the compressor section are also housed in the hub portion of the craft. Exhaust gases emitting from the turbine section are selectively ducted through annularly arranged, downwardly directed lift thrust producing ducts and/or rearwardly directed ducts or vanes for generation of forward propulsion. Directional control during hovering and low speed flight is by selective braking of one or the other of the rotors, and during high speed flight also by selective control of spoiler surfaces arranged in the upper and lower external surfaces of the craft.

    摘要翻译： 一种环形的径向气体燃气涡轮发动机和利用它们用于喷气推进的机载车辆。 发动机包括反向旋转转子和具有相对旋转的环形排相互啮合的压缩机叶片的压缩机部分，两个转子共同的环形燃烧部分，其中燃烧区域由相对旋转的转子壁限定，以及由环形 排列相反的排气涡轮叶片。 没有定子叶片存在于压缩机或涡轮机部分中。工艺包括中心毂，发动机转子在其上推力轴承上旋转，空气轴承相对于彼此保持转子公差，并且保持转子公差在上方和下方 发动机转子。 通向压缩机部分的进气导叶也容纳在工艺的轮毂部分中。 从涡轮部分排出的废气通过环形布置的向下指向的提升推力产生管道和/或向后定向的管道或叶片选择性地导管，以产生向前推进。 悬停和低速飞行期间的定向控制是通过选择性地制动一个或另一个转子，并且在高速飞行期间还可以通过选择性地控制布置在飞行器的上外表面和下外表面中的扰流板表面。